US6679063B2 - Combustion chamber head for a gas turbine - Google Patents
Combustion chamber head for a gas turbine Download PDFInfo
- Publication number
- US6679063B2 US6679063B2 US09/968,491 US96849101A US6679063B2 US 6679063 B2 US6679063 B2 US 6679063B2 US 96849101 A US96849101 A US 96849101A US 6679063 B2 US6679063 B2 US 6679063B2
- Authority
- US
- United States
- Prior art keywords
- combustion chamber
- metering panel
- heat shield
- cooling air
- sleeve
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Lifetime
Links
Images
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
- F23R3/04—Air inlet arrangements
- F23R3/10—Air inlet arrangements for primary air
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
- F23R3/283—Attaching or cooling of fuel injecting means including supports for fuel injectors, stems, or lances
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
- F23R3/60—Support structures; Attaching or mounting means
Definitions
- This invention relates to a gas turbine with at least one combustion chamber, a combustion chamber wall, a metering panel, at least one heat shield, at least one sleeve and a cowling.
- combustion chambers are of the one-part annular type made up of several, inseparably connected components.
- the main components are the inner and the outer combustion chamber wall and the combustion chamber head.
- the combustion chamber head is either made as a single component, for example by casting, or of different components, such as sheet-metal fabrications, turned parts etc.
- combustion chamber heads are known which are made up of individual components joined together by bolt-type fastenings or similar means.
- the known designs generally are characterized by a high assembly effort.
- assembly of the heat shield together with the sleeves to the metering panel is difficult with some of the known designs since it must be performed from the exit side of the combustion chamber. This involves a considerable increase of the assembly costs.
- combustion chamber heads have zones which are problematic in terms of the supply of cooling air, these problems arising from the circumstance that the individual components may compromise the supply of cooling air to the heat shield in certain zones.
- the sleeve and the heat shield form a unit and are assembled together on the metering panel from the exit of the combustion chamber.
- the surface of the sleeve which faces the combustion chamber interior is liable to considerable heating and cannot be cooled effectively.
- the present invention provides a combustion chamber head of the type specified at the beginning which combines simplicity of design and easy and cost-effective manufacture and assembly with the capability of effective cooling of the heat shield.
- a combustion chamber head for a gas turbine comprising: a combustion chamber outer wall; a combustion chamber inner wall; a metering panel; at least one heat shield; at least one sleeve; and a cowling; wherein the metering panel is formed as a unitary part with the combustion chamber outer wall and the combustion chamber inner wall, the heat shield is mounted to the metering panel from a downstream side of the metering panel, the sleeve is mounted to the metering panel from an upstream side of the metering panel, and the cowling is removably attached to the metering panel.
- the combustion chamber head according to this invention is characterized by a variety of merits.
- the heat shield is mounted to the metering panel from the downstream side, whilst all other components are fitted from the upstream side of the metering panel.
- This method of assembly is far simpler since it dispenses with the need of fitting and securing bolt-type fastenings or similar means from the side of the combustion chamber interior.
- the removable cowling provides for free, undisturbed access to the assembly areas. Providing the cowling as an extra, removable, separate component enables the entire combustion chamber head to be assembled without any problems. Moreover, it is not necessary to provide the cowling with assembly openings or similar means as known in the prior art. Rather, the present invention provides for free, unhindered access to the upstream side of the metering panel.
- a particularly favourable feature of the design according to the present invention is that the sleeves are installed from the upstream side of the metering panel. This feature provides for re-location of the sliding and sealing face away from the metering panel, enabling cooling air to reach also the inner areas of the heat shield without problems. This provides for more effective and improved cooling.
- the heat shield is provided with stud bolts which can be led through openings in the metering panel. Separate bolts or similar means are, therefore, dispensable. Attaching the stud bolts to the heat shield also ensures high operational safety by avoiding the risk of parts coming off and entering the combustion chamber interior during operation.
- the sleeve is preferably attached by means of retainers on the metering panel.
- these retainers are attached to the stud bolts of the heat shield. Additional bolts or threaded fastenings can, therefore, be entirely dispensed with. The entire construction is simplified considerably.
- each retainer holds two adjacent sleeves.
- At least one stud bolt is provided on the retainers.
- the cowling can simply be put onto the studs and bolted from the exterior.
- the metering panel is provided with a plurality of cooling air holes, as known in the state of the art.
- the heat shield can be favourable to provide it with a rim which abuts a collar of the sleeve, this rim extending in the upstream direction and being led through an opening in the metering panel.
- the height of the rim is selected such that, in the installed condition, the rim extends appropriately beyond the upstream side of the metering panel, thereby allowing the cooling air to freely access the central zone of the heat shield even if the collar of the sleeve abuts the cylindrical rim.
- the design according to the present invention enables a defined gap to be provided between the outer wall of the cylindrical rim of the sleeve and the inner wall of the rim of the heat shield, this gap permitting a radial and circumferential relative movement of a fuel nozzle and the combustion chamber head.
- the size of the collar of the sleeve exceeds the outer diameter of the rim of the heat shield by the max. possible amount of movement, this feature enabling the space before the metering panel to be sealed to the combustion chamber against undesired leakage air even if the max. possible movement of the sleeve should take place. This provides for advantageous assembly and operating conditions.
- the gaps between the sleeve and the retainers are particularly advantageous since they provide for sufficient clearance necessary for thermal compensation.
- the sleeve is securely and adequately positioned by the left or right part, respectively, of the adjacent retainers. Accordingly, each retainer secures two adjacent sleeves.
- the retainer itself is fitted to the stud bolts of the heat shield and secured to the metering panel with appropriate nuts.
- the retainer can accordingly also be designed as a support for the cowling, as already mentioned in the above.
- the design proposed in the present invention enables the individual components to be separately manufactured and safely assembled. This provides for a high degree of flexibility also in terms of the candidate manufacturing processes and materials.
- FIG. 1 is a design of a combustion chamber head in accordance with the state of the art
- FIG. 2 is a simplified sectional side view of an embodiment of a combustion chamber according to the present invention with a combustion chamber head according to the present invention
- FIG. 3 is an enlarged partial view of the combustion chamber head of FIG. 2,
- FIG. 4 is a sectional view of a combustion chamber head showing multiple heat shields and sleeves
- FIG. 5 is a perspective partial view similar to FIG. 4 of the upstream area of the metering panel with the multiple sleeves and retainers, and
- FIG. 6 is a simplified sectional side view of the metering panel and the heat shield showing the attachment of the heat shield by means of stud bolts.
- FIG. 1 shows the design according to the state of the art in which a combustion chamber outer wall 2 and a combustion chamber inner wall 3 forms a one-part design with a metering panel 1 . Also, the metering panel 1 forms one part with a cowling 6 .
- a heat shield 4 is fastened to the metering panel by means of bolts not further illustrated. The heat shield 4 also holds a sleeve 5 .
- a collar 16 on the sleeve 5 locates against the metering panel 1 with pre-tension provided by an interposed spacer 17 .
- a burner 15 is inserted in the sleeve 5 .
- this type of combustion chamber head is expensive and difficult to assemble.
- the cowling 6 must be provided with appropriate assembly openings (not shown) to enable the bolt-type fastenings to be made.
- the position of the sleeve 5 or the heat shield 4 , respectively, relative to the metering panel 1 is to be adjusted.
- the heat shield 4 is to be set by means of a washer 18 .
- FIGS. 2 to 6 illustrate an embodiment according to the present invention.
- FIG. 2 is a schematic sectional side view showing, in simplified representation, an annular combustion chamber with a combustion chamber outer wall 2 and a combustion chamber inner wall 3 .
- the metering panel 1 forms one part with the combustion chamber walls 2 and 3 and contains appropriate openings enabling cylindrical rims 13 of a heat shield 4 to be led through (ref. FIGS. 3 and 4 ).
- the rim 13 of the heat shield 4 extends upstream in the axial direction.
- a sleeve 5 with an annular collar 14 abuts the rim 13 of the heat shield 4 .
- the diameter of the collar 14 is designed such that the sleeve 5 can move in the sideward direction relative to the metering panel 1 or the heat shield 4 , respectively, without incurring the risk of undesired cooling air leakage.
- the heat shield 4 features several stud bolts 7 (of which only some are shown in FIG. 5 for clarity purposes).
- the stud bolts 7 pass through openings of the metering panel 1 and of the bases of the retainers 8 , thereby providing for a common bolt-type connection of the retainers 8 and of the heat shield 4 to the metering panel 1 .
- FIG. 6 is a sectional view, similar to FIG. 4, in which the sectional plane is passed through at least one of the stud bolts 7 of the heat shield 4 to elucidate the bolt-type connection of the heat shield 4 to the metering panel 1 by means of the stud bolts 7 with the retainers 8 interposed.
- each of the retainers 8 features a stud bolt 9 which serves for the attachment of the cowling 6 , as shown in FIG. 4 .
- the metering panel 1 contains annular grooves 11 (ref. FIG. 5 ), each accommodating a rim 10 of the cowling 6 (FIG. 3 ).
- the metering panel features a plurality of cooling air holes 12 , as known from the state of the art.
- the arrangement according to the present invention provides for sufficient spaces to supply cooling air to the heat shield 4 .
- the combustion chamber head provides for the supply of cooling air to the heat shield 4 through openings in the cowling 6 , both directly via the cooling air holes 12 of the metering panel 1 and, in the area of the sleeve 5 , via the spaces 19 formed by the rim 13 of the heat shield 4 and the collar 14 of the sleeve 5 beneath the retainer 8 through the cooling air holes 12 of the metering panel 1 .
- the design proposed in the present invention therefore, simplifies the assembly of the sleeves by providing a removable cowling. Furthermore, the cooling air for the heat shield can be supplied closely to the central bore of the heat shield. This provides for efficient cooling of all zones of the heat shield.
- the present invention also provides for a design of heat shield in which the air mass flow between the heat shield and the metering panel can be passed to the outside via the entire rearward surface of the heat shield, this air being used, on its further route, as starter film for the combustion chamber walls. Accordingly, the benefits of this invention are, on the one hand, the simplified assembly which results in a considerable reduction of costs and, on the other hand, the improved cooling of the heat shield which results in an increase of life and a saving of cooling air.
- the cooling air which is saved over the state of the art can, for instance, be integrated in the combustion process, this resulting in an additional pollutant reduction.
- the present invention relates to a combustion chamber head for a gas turbine with at least one combustion chamber wall 2 , 3 , a metering panel 1 , at least one heat shield 4 , at least one sleeve 5 and a cowling 6 , characterized in that the metering panel 1 forms one part with the combustion chamber outer wall 2 and the combustion chamber inner wall 3 , in that the heat shield 4 is mounted onto the metering panel 1 from the downstream side of the metering panel 1 , in that the sleeve 5 is mounted to the metering panel 1 from the upstream side, and in that the cowling 6 is separably (removably) attached to the metering panel 1 .
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Portable Nailing Machines And Staplers (AREA)
- Cylinder Crankcases Of Internal Combustion Engines (AREA)
- Supercharger (AREA)
Abstract
Description
Claims (23)
Applications Claiming Priority (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE10048864.1 | 2000-10-02 | ||
DE10048864 | 2000-10-02 | ||
DE10048864A DE10048864A1 (en) | 2000-10-02 | 2000-10-02 | Combustion chamber head for a gas turbine |
Publications (2)
Publication Number | Publication Date |
---|---|
US20020038549A1 US20020038549A1 (en) | 2002-04-04 |
US6679063B2 true US6679063B2 (en) | 2004-01-20 |
Family
ID=7658490
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US09/968,491 Expired - Lifetime US6679063B2 (en) | 2000-10-02 | 2001-10-02 | Combustion chamber head for a gas turbine |
Country Status (3)
Country | Link |
---|---|
US (1) | US6679063B2 (en) |
EP (1) | EP1193451B1 (en) |
DE (2) | DE10048864A1 (en) |
Cited By (28)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20060042271A1 (en) * | 2004-08-27 | 2006-03-02 | Pratt & Whitney Canada Corp. | Combustor and method of providing |
US20080115499A1 (en) * | 2006-11-17 | 2008-05-22 | Patel Bhawan B | Combustor heat shield with variable cooling |
US20080115506A1 (en) * | 2006-11-17 | 2008-05-22 | Patel Bhawan B | Combustor liner and heat shield assembly |
US20080115498A1 (en) * | 2006-11-17 | 2008-05-22 | Patel Bhawan B | Combustor liner and heat shield assembly |
US20080229750A1 (en) * | 2007-03-22 | 2008-09-25 | Rolls-Royce Plc | Location ring arrangement |
US20080236169A1 (en) * | 2007-03-30 | 2008-10-02 | Eduardo Hawie | Combustor floating collar with louver |
US20080282703A1 (en) * | 2007-05-16 | 2008-11-20 | Oleg Morenko | Interface between a combustor and fuel nozzle |
US20110000216A1 (en) * | 2009-07-06 | 2011-01-06 | Kawasaki Jukogyo Kabushiki Kaisha | Gas turbine combustor |
US20110265483A1 (en) * | 2009-10-28 | 2011-11-03 | Man Diesel & Turbo Se | Combustor For A Turbine, and Gas Turbine Outfitted With A Combustor of This Kind |
US20140318148A1 (en) * | 2013-04-30 | 2014-10-30 | Rolls-Royce Deutschland Ltd & Co Kg | Burner seal for gas-turbine combustion chamber head and heat shield |
US8943835B2 (en) * | 2010-05-10 | 2015-02-03 | General Electric Company | Gas turbine engine combustor with CMC heat shield and methods therefor |
US9021812B2 (en) | 2012-07-27 | 2015-05-05 | Honeywell International Inc. | Combustor dome and heat-shield assembly |
US9021675B2 (en) | 2011-08-15 | 2015-05-05 | United Technologies Corporation | Method for repairing fuel nozzle guides for gas turbine engine combustors using cold metal transfer weld technology |
US9222675B2 (en) | 2011-03-24 | 2015-12-29 | Rolls-Royce Deutschland Ltd & Co Kg | Combustion chamber head with holding means for seals on burners in gas turbines |
US20160010869A1 (en) * | 2014-07-09 | 2016-01-14 | Rolls-Royce Deutschland Ltd & Co Kg | Combustion chamber of a gas turbine with bolted combustion chamber head |
US9328926B2 (en) | 2011-03-22 | 2016-05-03 | Rolls-Royce Deutschland Ltd & Co Kg | Segmented combustion chamber head |
US20170167731A1 (en) * | 2015-12-11 | 2017-06-15 | Rolls Royce Deutschland Ltd & Co Kg | Method for mounting a combustion chamber of a gas turbine engine |
US20170176004A1 (en) * | 2015-12-18 | 2017-06-22 | Pratt & Whitney Canada Corp. | Combustor floating collar assembly |
US9803869B2 (en) | 2014-03-11 | 2017-10-31 | Rolls-Royce Deutschland Ltd & Co Kg | Gas turbine combustion chamber and method for manufacturing the same |
US9958159B2 (en) | 2013-03-13 | 2018-05-01 | Rolls-Royce Corporation | Combustor assembly for a gas turbine engine |
US20180356095A1 (en) * | 2017-03-06 | 2018-12-13 | General Electric Company | Combustion Section of a Gas Turbine Engine |
US10378775B2 (en) | 2012-03-23 | 2019-08-13 | Pratt & Whitney Canada Corp. | Combustor heat shield |
US10408456B2 (en) * | 2015-10-29 | 2019-09-10 | Rolls-Royce Plc | Combustion chamber assembly |
US10859271B2 (en) | 2017-09-22 | 2020-12-08 | Rolls-Royce Plc | Combustion chamber |
US11428410B2 (en) | 2019-10-08 | 2022-08-30 | Rolls-Royce Corporation | Combustor for a gas turbine engine with ceramic matrix composite heat shield and seal retainer |
US11466858B2 (en) | 2019-10-11 | 2022-10-11 | Rolls-Royce Corporation | Combustor for a gas turbine engine with ceramic matrix composite sealing element |
US11892165B2 (en) | 2021-05-19 | 2024-02-06 | General Electric Company | Heat shield for fuel nozzle |
US12123592B2 (en) | 2022-01-12 | 2024-10-22 | General Electric Company | Fuel nozzle and swirler |
Families Citing this family (10)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US9188341B2 (en) * | 2008-04-11 | 2015-11-17 | General Electric Company | Fuel nozzle |
DE102013222863A1 (en) | 2013-11-11 | 2015-05-13 | Rolls-Royce Deutschland Ltd & Co Kg | Gas turbine combustor and method for its production |
DE102015212573A1 (en) * | 2015-07-06 | 2017-01-12 | Rolls-Royce Deutschland Ltd & Co Kg | Gas turbine combustor with integrated turbine guide wheel and method for its production |
DE102015213629A1 (en) | 2015-07-20 | 2017-01-26 | Rolls-Royce Deutschland Ltd & Co Kg | Cover member and combustion chamber assembly for a gas turbine |
GB201701380D0 (en) | 2016-12-20 | 2017-03-15 | Rolls Royce Plc | A combustion chamber and a combustion chamber fuel injector seal |
US10378770B2 (en) * | 2017-01-27 | 2019-08-13 | General Electric Company | Unitary flow path structure |
CN107575889B (en) * | 2017-09-05 | 2023-05-16 | 中国联合重型燃气轮机技术有限公司 | Fuel nozzle of gas turbine |
US10823419B2 (en) * | 2018-03-01 | 2020-11-03 | General Electric Company | Combustion system with deflector |
US11125436B2 (en) * | 2019-07-03 | 2021-09-21 | Pratt & Whitney Canada Corp. | Combustor floating collar mounting arrangement |
FR3112382B1 (en) * | 2020-07-10 | 2022-09-09 | Safran Aircraft Engines | ANNULAR COMBUSTION CHAMBER FOR AN AIRCRAFT TURBOMACHINE |
Citations (20)
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DE2944139A1 (en) | 1978-11-03 | 1980-05-14 | Gen Electric | BURNER ARRANGEMENT |
US4262486A (en) * | 1978-08-19 | 1981-04-21 | Rolls-Royce Limited | Combustion chambers |
GB2073401A (en) | 1980-04-02 | 1981-10-14 | United Technologies Corp | Fuel nozzle guide heatshield for a gas turbine engine |
GB2107448A (en) | 1980-10-21 | 1983-04-27 | Rolls Royce | Gas turbine engine combustion chambers |
US4458479A (en) * | 1981-10-13 | 1984-07-10 | General Motors Corporation | Diffuser for gas turbine engine |
GB2247522A (en) | 1990-09-01 | 1992-03-04 | Rolls Royce Plc | Gas turbine engine combustor |
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EP0604021A1 (en) | 1992-12-21 | 1994-06-29 | United Technologies Corporation | Individually removable combustor liner panel for a gas turbine engine |
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US5419115A (en) | 1994-04-29 | 1995-05-30 | United Technologies Corporation | Bulkhead and fuel nozzle guide assembly for an annular combustion chamber |
US5524430A (en) | 1992-01-28 | 1996-06-11 | Societe National D'etude Et De Construction De Moteurs D'aviation S.N.E.C.M.A. | Gas-turbine engine with detachable combustion chamber |
DE19515537A1 (en) | 1995-04-27 | 1996-10-31 | Bmw Rolls Royce Gmbh | Head part of a gas turbine annular combustion chamber |
US5623827A (en) * | 1995-01-26 | 1997-04-29 | General Electric Company | Regenerative cooled dome assembly for a gas turbine engine combustor |
EP0841520A2 (en) | 1996-11-07 | 1998-05-13 | ROLLS-ROYCE plc | Gas turbine engine combustor |
EP0927854A2 (en) | 1997-12-31 | 1999-07-07 | United Technologies Corporation | Low nox combustor for gas turbine engine |
US5924288A (en) | 1994-12-22 | 1999-07-20 | General Electric Company | One-piece combustor cowl |
US5956955A (en) | 1994-08-01 | 1999-09-28 | Bmw Rolls-Royce Gmbh | Heat shield for a gas turbine combustion chamber |
US6412272B1 (en) * | 1998-12-29 | 2002-07-02 | United Technologies Corporation | Fuel nozzle guide for gas turbine engine and method of assembly/disassembly |
-
2000
- 2000-10-02 DE DE10048864A patent/DE10048864A1/en not_active Withdrawn
-
2001
- 2001-09-20 EP EP01122467A patent/EP1193451B1/en not_active Expired - Lifetime
- 2001-09-20 DE DE50105179T patent/DE50105179D1/en not_active Expired - Lifetime
- 2001-10-02 US US09/968,491 patent/US6679063B2/en not_active Expired - Lifetime
Patent Citations (23)
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US4262486A (en) * | 1978-08-19 | 1981-04-21 | Rolls-Royce Limited | Combustion chambers |
GB2034874A (en) | 1978-11-03 | 1980-06-11 | Gen Electric | Gas turbine engine combustor |
DE2944139A1 (en) | 1978-11-03 | 1980-05-14 | Gen Electric | BURNER ARRANGEMENT |
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Cited By (45)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US7308794B2 (en) * | 2004-08-27 | 2007-12-18 | Pratt & Whitney Canada Corp. | Combustor and method of improving manufacturing accuracy thereof |
US20060042271A1 (en) * | 2004-08-27 | 2006-03-02 | Pratt & Whitney Canada Corp. | Combustor and method of providing |
US7721548B2 (en) | 2006-11-17 | 2010-05-25 | Pratt & Whitney Canada Corp. | Combustor liner and heat shield assembly |
US20080115499A1 (en) * | 2006-11-17 | 2008-05-22 | Patel Bhawan B | Combustor heat shield with variable cooling |
US20080115506A1 (en) * | 2006-11-17 | 2008-05-22 | Patel Bhawan B | Combustor liner and heat shield assembly |
US20080115498A1 (en) * | 2006-11-17 | 2008-05-22 | Patel Bhawan B | Combustor liner and heat shield assembly |
US7748221B2 (en) | 2006-11-17 | 2010-07-06 | Pratt & Whitney Canada Corp. | Combustor heat shield with variable cooling |
US7681398B2 (en) | 2006-11-17 | 2010-03-23 | Pratt & Whitney Canada Corp. | Combustor liner and heat shield assembly |
US20080229750A1 (en) * | 2007-03-22 | 2008-09-25 | Rolls-Royce Plc | Location ring arrangement |
US20080236169A1 (en) * | 2007-03-30 | 2008-10-02 | Eduardo Hawie | Combustor floating collar with louver |
US7861530B2 (en) * | 2007-03-30 | 2011-01-04 | Pratt & Whitney Canada Corp. | Combustor floating collar with louver |
US7926280B2 (en) * | 2007-05-16 | 2011-04-19 | Pratt & Whitney Canada Corp. | Interface between a combustor and fuel nozzle |
US20080282703A1 (en) * | 2007-05-16 | 2008-11-20 | Oleg Morenko | Interface between a combustor and fuel nozzle |
US8511088B2 (en) * | 2009-07-06 | 2013-08-20 | Kawasaki Jukogyo Kabushiki Kaisha | Gas turbine fuel injector mounting system |
US20110000216A1 (en) * | 2009-07-06 | 2011-01-06 | Kawasaki Jukogyo Kabushiki Kaisha | Gas turbine combustor |
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Also Published As
Publication number | Publication date |
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EP1193451A2 (en) | 2002-04-03 |
US20020038549A1 (en) | 2002-04-04 |
DE50105179D1 (en) | 2005-03-03 |
EP1193451A3 (en) | 2002-05-15 |
EP1193451B1 (en) | 2005-01-26 |
DE10048864A1 (en) | 2002-04-11 |
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